CN110562467A - Engine exhaust method of backward-pushing propeller - Google Patents
Engine exhaust method of backward-pushing propeller Download PDFInfo
- Publication number
- CN110562467A CN110562467A CN201810566968.9A CN201810566968A CN110562467A CN 110562467 A CN110562467 A CN 110562467A CN 201810566968 A CN201810566968 A CN 201810566968A CN 110562467 A CN110562467 A CN 110562467A
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- Prior art keywords
- propeller
- air guide
- engine
- pipe
- guide ring
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention discloses an engine exhaust method of a back-push propeller.A waste gas object exhausted by an engine exhaust pipe is exhausted to one side of the propeller, which is not close to an engine, through an air guide device, and the waste gas object does not contact with the propeller in the exhaust process. Different from the traditional direct exhaust mode of engine exhaust, the engine exhaust of the invention is directly exhausted behind the propeller through the gas guide ring pipe, and does not pollute the surface of the propeller blade; the exhaust pipe of the invention directly extends into the air guide ring pipe at the root of the blade through the air guide pipe and is not exposed outside the machine body; the waste gas is directly discharged from the rear part of the propeller, and the parts such as a machine body or a blade and the like are not polluted.
Description
Technical Field
The invention relates to an aircraft power system, in particular to an engine exhaust method of a back-push propeller.
background
The piston type aircraft engine is a reciprocating internal combustion engine for providing flight power for an aircraft, and the principle of the engine is to drive propellers such as an air propeller and the like to rotate to generate propulsive force. The aviation piston engine has the characteristics of low oil consumption, light weight, wide power range and the like, and is widely applied to aviation aircrafts such as small and medium-sized unmanned aerial vehicles, coaches and the like.
The existing push-back piston type aircraft engine mostly adopts a downward exhaust pipe, the exhaust pipe is positioned in front of a propeller, and in order to prevent exhaust pipe waste gas and waste residue from polluting an engine body, the exhaust pipe generally extends outwards for a certain distance. Although the design of the exhaust of the back-push type propeller piston engine avoids the pollution to the engine body, the following new problems are obviously brought about:
Firstly, the method comprises the following steps: because the propeller is arranged behind the engine through the back-push type power design, the diameter of the blade is large, waste gas discharged by the exhaust pipe is difficult to avoid the blade, and the waste gas discharged by the exhaust pipe pollutes the propeller and is attached to the surface of the blade, so that the performance of the propeller is reduced;
Secondly, the method comprises the following steps: because the exhaust pipe extends downwards or laterally for a certain distance, the machine body is directly exposed, the windward area is increased, and the resistance is increased;
thirdly, the method comprises the following steps: waste residues discharged by the exhaust pipe are attached to positions such as a propeller and a machine body, and need to be carefully cleaned after each flight is finished, so that later maintenance is complicated;
Fourthly: the propeller blades are covered with a large amount of waste residues, the propeller propelling efficiency is reduced, and the exposed exhaust pipes increase the flight resistance, which increases the oil consumption rate of the airplane during cruising and reduces the cruising time.
Disclosure of Invention
The invention aims to provide an engine exhaust method of a back-push type propeller, which is characterized in that waste gas of an engine passes through the propeller and is exhausted to the back of the propeller, the propulsion efficiency of the propeller is maintained, the windward resistance of an exhaust pipe is eliminated, the use and maintenance difficulty is reduced, and the flight cruising time is prolonged.
In order to achieve the purpose, the invention adopts the following technical scheme:
An engine exhaust method of a push-back propeller is characterized in that exhaust gas discharged from an exhaust pipe of the engine is discharged to the side, not close to the engine, of the propeller through an air guide device.
in the above solution, the exhaust gas does not contact the propeller during the exhaust process.
In the technical scheme, the air guide device comprises an air guide ring pipe which is arranged between the propeller and the engine and is communicated, the engine exhaust pipe is connected with an air guide pipe, and the other end of the air guide pipe fixedly extends into the ring pipe matched with the air guide ring pipe.
In the technical scheme, the air guide ring pipe is coaxially arranged with the rotating shaft and the propeller of the engine, and the air guide ring pipe and the output shaft of the engine and the propeller rotate coaxially.
in the technical scheme, the diameter of the inner ring of the air guide ring pipe ring belt is directly larger than the diameter of the connecting part of the air guide ring pipe and the propeller, and the other ring belts are communicated from one end to the other end except the position of the air guide ring pipe, which is in contact with the propeller surface of the propeller.
In the technical scheme, the connecting surface of the inner ring of the air guide ring pipe ring belt is contacted with the connecting surface of the propeller, and the connecting surface of the outer ring of the air guide ring pipe ring belt is in sealing contact with the connecting surface of the propeller.
In the technical scheme, the tail end of the air duct extends into the ring belt of the air duct ring, but the air duct does not contact with two walls of the ring belt of the air duct ring.
In the technical scheme, when the air guide ring pipe rotates at a high speed along with the propeller, the position of the air guide pipe is fixed, and the air guide pipe does not rotate along with the propeller and the air guide ring pipe.
In the technical scheme, the air guide device comprises two air guide ring pipes which are coaxial with the engine rotating shaft, clamp the propeller and are integrated with the propeller, the engine exhaust pipe is connected with an air guide pipe, and the other end of the air guide pipe fixedly extends into the ring belt matched with the air guide ring pipes.
In the technical scheme, the two air guide circular pipes are symmetrically arranged on two sides of the propeller and are connected with the two air guide circular pipes in a locking manner through the fastening pieces, the propeller is locked in the two annular air guides, and the fastening pieces are not in contact with the propeller.
in summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
Different from the traditional direct exhaust mode of engine waste gas, the waste gas and waste residue of the engine are directly exhausted behind the propeller through the gas guide ring pipe without polluting the surface of the propeller blade, so that the surface smoothness of the propeller blade is not affected, and the propulsion efficiency can still maintain a higher level;
Different from the traditional engine exhaust pipe which directly extends out of the engine body, the exhaust pipe of the invention directly extends into the air guide ring pipe at the root part of the blade through the air guide pipe, and is not exposed out of the engine body, thus eliminating windward resistance caused by the exposure of the exhaust pipe;
different from the traditional method that the propeller and the engine body are directly polluted by waste gas and waste residues of the engine, the waste gas and waste residues are directly discharged from the rear part of the propeller, the engine body or parts such as the blades are not polluted, and only the air guide ring pipe at the root part of the blade needs to be cleaned after the engine is used, so that the difficulty in use and maintenance of the engine body is reduced;
Because the surfaces of the propeller blades are not polluted by the waste gas and waste residue of the engine, the propeller can maintain higher propelling efficiency, and the exhaust pipe does not generate windward resistance, so that the oil consumption rate of the engine is reduced, and the cruising time is increased.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of the structure;
FIG. 2 is a front view of the propeller and the vicinity of the root;
FIG. 3 is a front view of the airway tube;
FIG. 4 is an exploded view of the structure of the propeller and airway tube;
wherein: 1 is an engine; 2 is an exhaust pipe; 3 is an air duct; 4 is a propeller; 5 is an air guide ring pipe, 5-1 is a connecting surface, 5-2 is a through part, and 6 is a fastening piece.
Detailed Description
all of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
in order to implement the solution according to the invention, the airway collar is used as shown in fig. 3, so that the cuff is not a complete circle in order to ensure proper functioning and fixation of the airway collar. When the air guide collar is fixedly connected with the propeller, the air guide collar must be designed into a structure capable of being buckled so as to be completely clamped on the propeller, because the air guide collar cannot be directly fixed on the propeller by fasteners such as screws.
the air guide ring pipe is a structure which is not available on the original propeller, so that the design of the air guide ring pipe is considered firstly, and new aerodynamic problems can not be brought to the propeller. Therefore, the position of the gas guide ring pipe is designed at the root of the propeller and is coaxially arranged with the rotation center of the propeller, so that the influence of the gas guide ring pipe on the airflow of the propeller in the rotation process is reduced. As shown in fig. 2, the gas guiding ring pipe is connected with the propeller and only has a small part of the center acting on the propeller, so that the work of the propeller is not influenced. The air guide ring pipe can be in a structure of being communicated with the center in a circular mode, and the propeller and the air guide ring pipe are fixed into a whole and then fixedly connected with an output shaft of the engine in the installation process, so that the synchronous rotation of the air guide ring pipe and the propeller is guaranteed.
The air guide ring pipe comprises two parts, namely a through part and a connecting surface for connecting with the propeller, when the air guide ring pipe is locked with the propeller, one part of the air guide ring pipe exceeds the root part of the propeller, and the part of the air guide ring pipe exceeds the through ring belt, namely the inner diameter of the ring belt of the air guide ring pipe is necessarily larger than the minimum diameter of the connecting part of the root part of the propeller, as shown in figure 2, the diameter of the ring belt inner ring of the air guide ring pipe is consistent with the connecting surface of the propeller, and the diameter of the outer ring is larger than the connecting surface diameter of the propeller. Thus, the portion of the entire annulus that connects to the propeller-connecting face is a closed face, while the other portions are through portions, so that gas can pass through from one face to the other.
Example one
as shown in fig. 1, a gas guide ring pipe is arranged between the engine and the propeller, and the gas guide ring pipe and the propeller are fixed with an output shaft of the engine into a whole by connecting and fixing reeds; the air outlet of the exhaust pipe of the engine is connected with an air duct, the other end of the air duct extends into the air guide ring pipe, the air duct does not contact with the inner wall and the outer wall of the air guide ring pipe at all, and when the propeller and the air guide ring pipe rotate at high speed, the position of the air duct is fixed and does not rotate along with the propeller and the air guide ring pipe. The waste gas and waste residue discharged from the engine exhaust pipe are directly discharged to the rear end of the propeller through the gas guide ring pipe, namely the propeller is not close to one side of the engine, and the problem that the traditional waste gas is directly sprayed to the propeller is thoroughly solved.
Example two
As shown in fig. 4, the gas guide ring pipe includes two symmetrical parts respectively disposed at both sides of the propeller, the shape of the end surface of the gas guide ring pipe connected to the propeller must be identical to the connecting surface of the screw member, and when the gas guide ring pipe is attached to the connecting surface of the screw member, it is ensured that the gas guide ring pipe is completely attached to the propeller. The two divided air guide ring pipes are two completely symmetrical parts, when the propellers are clamped between the two parts, the air guide ring pipes of the two parts are fixed and locked by screws, so that the air guide ring pipes and the propellers are completely clamped and clamped, and the air guide ring pipes and the propellers are integrated.
whereas the air duct in fig. 1 and 4 extends into the annulus of the through air duct ring, when the propeller is rotating at high speed, the air duct is stationary, i.e. stationary relative to the propeller, and the exhaust gases from the engine are led directly into the air duct ring via the air duct and are discharged directly out of the propeller via the through annulus. That is, the exhaust gas discharged from the engine is not directly injected toward the propeller but is directly discharged from the root of the propeller through the air guide ring duct, and the exhaust gas is discharged into the air without any contact with the blade surface of the propeller at all during the discharge.
The number of exhaust pipes of the engine is not limited in the embodiment, and the exhaust function can be realized as long as the final air guide pipes extend into the through ring belt of the air guide ring pipe.
The embodiment does not limit the completely symmetrical air guide ring pipe, and the exhaust gas discharged from the exhaust pipe of the engine can be discharged to the side of the propeller, which is not close to the engine, through one air guide device as long as the final exhaust gas is led out from the through ring belt at the root part of the blade.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (10)
1. The engine exhaust method of the push-back propeller is characterized in that the exhaust gas discharged from the exhaust pipe of the engine is discharged to the side of the propeller not close to the engine through an air guide device.
2. A method of exhausting an engine with a pushback propeller as claimed in claim 1, wherein said exhaust is not in contact with the propeller during the exhaust.
3. The engine exhaust method of the backward pushing type propeller as claimed in claim 1 or 2, wherein the air guide device comprises an air guide ring pipe which is arranged between the propeller and the engine and is communicated with the engine, an air guide pipe is connected to the engine exhaust pipe, and the other end of the air guide pipe is fixedly extended into the ring belt of the air guide ring pipe.
4. The engine exhaust method of a pushback propeller as claimed in claim 3, wherein said air guide collar is coaxially disposed with the output shaft of the engine and the propeller, and the air guide collar is integrally and coaxially rotated with the output shaft of the engine and the propeller.
5. The method as claimed in claim 3, wherein the inner ring of the air guide ring pipe is directly larger than the diameter of the connection part of the propeller, and the air guide ring pipe is connected from one end to the other end except the position where the air guide ring pipe contacts the propeller surface of the propeller.
6. the engine exhaust method of the pushback propeller as claimed in claim 5, wherein the connecting surface of the inner ring of the air guide ring band is in contact with the connecting surface of the propeller, and the connecting surface of the outer ring of the air guide ring band is in sealing contact with the connecting surface of the propeller.
7. The method of claim 3, wherein the end of the air duct extends into the cuff of the airway tube, but the air duct does not contact the two walls of the cuff of the airway tube.
8. The method as claimed in claim 7, wherein the air guide tube is fixed in position and does not rotate with the propeller and the air guide ring when the air guide ring rotates with the propeller at a high speed.
9. the engine exhaust method of the backward pushing type propeller as claimed in claim 1 or 2, wherein the air guide device comprises two air guide ring pipes which are coaxial with the engine output shaft, clamp the propeller and are integrated with the propeller, the engine exhaust pipe is connected with an air guide pipe, and the other end of the air guide pipe is fixedly extended into the ring belt matched with the air guide ring pipe.
10. The engine exhaust method of a pushback propeller as claimed in claim 9, wherein said two air guide collars are symmetrically disposed at both sides of the propeller, and are locked and connected to each other by a fastening member, and the two annular air guides lock the propeller therein, and said fastening member does not contact with the propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810566968.9A CN110562467A (en) | 2018-06-05 | 2018-06-05 | Engine exhaust method of backward-pushing propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810566968.9A CN110562467A (en) | 2018-06-05 | 2018-06-05 | Engine exhaust method of backward-pushing propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110562467A true CN110562467A (en) | 2019-12-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810566968.9A Pending CN110562467A (en) | 2018-06-05 | 2018-06-05 | Engine exhaust method of backward-pushing propeller |
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| Country | Link |
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| CN (1) | CN110562467A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101462596A (en) * | 2009-01-12 | 2009-06-24 | 北京航空航天大学 | Tail wing connection structure suitable for small-sized unmanned plane with tailboom |
| CN101837835A (en) * | 2010-05-26 | 2010-09-22 | 中兵光电科技股份有限公司 | Unmanned aerial vehicle system applied to weather modification |
| CN203612198U (en) * | 2013-11-05 | 2014-05-28 | 桂林鑫鹰电子科技有限公司 | Front-pull rear-push type multifunctional fixed-wing unmanned aerial vehicle |
-
2018
- 2018-06-05 CN CN201810566968.9A patent/CN110562467A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101462596A (en) * | 2009-01-12 | 2009-06-24 | 北京航空航天大学 | Tail wing connection structure suitable for small-sized unmanned plane with tailboom |
| CN101837835A (en) * | 2010-05-26 | 2010-09-22 | 中兵光电科技股份有限公司 | Unmanned aerial vehicle system applied to weather modification |
| CN203612198U (en) * | 2013-11-05 | 2014-05-28 | 桂林鑫鹰电子科技有限公司 | Front-pull rear-push type multifunctional fixed-wing unmanned aerial vehicle |
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Application publication date: 20191213 |